R E MOT E AUT ONOMOUS MAPPING OF RADIO F R E QUE NCY OBST - PowerPoint PPT Presentation

R E MOT E AUT ONOMOUS MAPPING OF RADIO F R E QUE NCY OBST R UCT ION DE VICE S e am: Jo rg e n Ba e rtsc h, I a n Co o ke , K e nne dy Ha rrma nn, Ma ry L a ndis, T Sa ra h L a rso n, Ha rrisio n Ma st, E tha n Mo rg a n, Se lb y Sto ut, Ja ke Urse tta , Justin Willia ms, Sa ma ntha Willia ms : De nnis Ako s Sponsor : Ja de Mo rto n Advisor

St Step 1: 1: St Step 3: 3: Step 5: St CONOPS Launch UA Launch UAS wi with pa payloa oad Simulate GP Si GPS de denied env environment nment Transmit signal strength and Tr ov over de design gnate ted ar area ea pos positi tion oning m g measurements ts to gr to grou ound GPS 3 km km Denied UAS UA 5 3 500 m 500 GPS Signal Strength 3 km Autopilot 1 Operational km Communication Payload 6 4 2 Autopilot Communication St Step 2: St Step 4: Step 6: St St Start autonomous flight on pre- Collect data on signal strength Co Land UAS and Land and local calize e signal nal planned pl d pa path th so source at ground st statio ion Ground Gr d Payload GPS Denied Area St Station Receiver CDR 2 Signal Source

I NT E GRAT I VE T E ST I NG PROBL E MS T he use of GPS T he T alon will not Pr oblem jammer s is illegal mesaur e fr equenc ies outside of the GPS band Use a WiF i sig na l to T he “Disc o ” UAS will So lutio n simula te GPS b e use d to sa mple ja mme r WiF i po we r o ve r the GPS de nie d a re a Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults 3 E ng ine e ring Ma na g e me nt

PARROT DI SCO UAS Give n to te am RAMROD • by c usto me r Alre ady pro ve n • c apable o f sampling WiF i po we r Will be use d to c re ate • c o nto urplo t o f signal po we r Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults 4 E ng ine e ring Manag e me nt

Disco WiF i Sampling 500 m 500 GPS Signal Strength Dis Disco GPS Denied Area CDR 5 Signal Source

Disc o WiF i Contour Map 500 m 500 Dis Disco GPS Denied Area CDR 6 Signal Source

St Step 1: St Step 3: Step 5: St 5: CONOPS Tr Transmit sig signal st strength and and Launch UAS with Launch h pay ayload ad Simulate GPS Si PS denied environment ov over de design gnated a d area pos positi tion oning meas measur urement ements to to gr grou ound GPS 3 km km Denied UA UAS 500 m 500 3 km Autopilot Operational km Communication Payload Autopilot Communication St Step 2: Step 4: St 4: Step 6: St 6: Land La nd UA UAS and post pr process po position/wi wifi St Start autonomous flight on pre- Co Collect data for actual and signal at si at gr grou ound st station planned pl d pa path th estimat es mated ed locat cation n with h Tal alon Gr Ground d Payload GPS Denied Area Station St Receiver CDR 7 Signal Source

CRI T I CAL PROJE CT E L E ME NT S CPE De sc r iption Re ason GPS De nie d Maintain auto no mo us flig ht while in a A PPD o r E T will c ause GPS data to be F lig ht So ftware simulate d GPS de nie d e nviro nme nt fo r up to inac c urate . 200 se c o nds at a time UAS Use the T alo n to fly in a simulate d GPS A UAS c apable o f suppo rting the de nie d e nviro nme nt while ho using the ne c e ssary se nso rs wo uld be the be st o pe ratio nal paylo ad made by te am me ans o f c o ve ring the re quire d are a. RAMROD Paylo ad Se lf-po we re d se nso r paylo ad that c an T o me asure the RF so urc e all ne c e ssary mo nito r, sto re and transmit RF I sig nal data se nso rs must be inte g rate d to g e the r. By while inte rfac e d with the UAS platfo rm c usto me r re que st the paylo ad must be c apable o f taking RF me asure me nts witho ut UAS inte g ratio n Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults 8 E ng ine e ring Ma na g e me nt

L E VE L S OF SUCCE SS Ope r ational UAS Platfor m GPS De nie d F light R F L oc alization Payload Softwar e L e ve l 1 -Co lle c t a nd sto re -Sha ll use ma nua l flig ht -Auto pilo t switc he s -Sha ll b e a b le to po we r to a c hie ve a minimum se a mle ssly to GPS e sta b lish a n RF I me a sure me nts fo r a to ta l flig ht time o f 60 de nie d flig ht po we r pro file full 60 minute s minute s while c o nta ining the full pa ylo a d L e ve l 2 -T ra nsmit da ta up to -Sha ll ha ve the a b ility to -Sha ll a llo w fo r -L o c a lize RF I so urc e 4.25 km using L T E fly a uto no mo usly fo r 60 ma inta ine d stra ig ht a nd within 100 m c o nne c tio n. minute s with GPS a c tive le ve l GPS de nie d flig ht -Co mmunic a te fo r 1 km po we r da ta with PixHa wk L e ve l 3 -Sha ll ha ve the a b ility to -Sha ll a llo w fo r turning -L o c a lize RF I so urc e fly a uto no mo usly fo r 10 ma nue ve rs in GPS within 40 m minute s with GPS de nie d de nie d c o nditio ns -Sha ll ke e p po sitio na l e rro r le ss tha n 30m a fte r 2km o f GPS de nie d flig ht Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults 9 E ng ine e ring Ma na g e me nt

DE SI GN Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults E ng ine e ring Ma na g e me nt 10

F UNCT I ONAL BL OCK DI AG RAM Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults 11 E ng ine e ring Ma na g e me nt

CRI T I CAL F OR MI SSI ON SUCCE SS Cr itic al Components Chosen R eason Component is Mission Cr itic al Component F lig ht Co ntro lle r (PixHa wk) • F lig ht Co ntro lle r PixHa wk 2.1 Co ntro ls a ll flig ht c ha ra c te ristic s a nd ma na g e s a uto no mo us flig ht • Co nta ins mo d ifie d GPS-De nie d F lig ht Mo d e I ne rtia l • I ne rtia l DMU11 Ma in c o mpo ne nt fo r minimizing po sitio na l Me a sure me nt Me a sure me nt Unit e rro r in GPS-De nie d F lig ht Mo d e Unit (DMU11) • Sig na l F ilte r NT 1065 Co lle c ts ra w po we r d a ta o n L 1 a nd L 2 b a nd s Sig na l F ilte r a nd filte rs it into usa b le d a ta fo r (NT 1065) mic ro pro c e sso r • Mic ro pro c e sso r Mic ro pro c e sso r Mic ro Ze d Se nd s a ll po we r a nd po sitio n d a ta to the g ro und (Mic ro Ze d) • Sto re s a ll po we r d a ta • I nd ic a te s flig ht mo d e switc h Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults 12 E ng ine e ring Ma na g e me nt

PAYL OAD BASE L I NE DE SI GN E the rne t Ke y Par ame te r Value Output to Ce ll Mo de m Mic ro pro c e sso r Size (c m) 7.62x13.21x6.98 Ma ss (g ) 450 Sig na l F ilte r Avg . Da ta Uplo a d: 7.64 T ra nsmissio n Pa ylo a d Ra te (Mb ps) Do wnlo a d: 6.67 Struc ture 6.98 c m Ba tte ry 13.2 c m Ba tte ry 7.62 c m Bra c ke t Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults 13 E ng ine e ring Ma na g e me nt

UAS BASE L I NE DE SI GN Px4 Optic a l F lo w HD Ca me ra a nd Mo to r a nd E SC T wo 7000mAh L iDAR PixHa wk F lig ht Ope ra tio na l Pa ylo a d Ca me ra Mo unt Pro pe lle r Ba tte rie s Co ntro lle r 8.9 c m 49 c m Ke y Par ame te r Value Ke y Par ame te r Value Wing spa n (m) 1.7 F ina l CG 55 mm a ft o f le a ding L o c a tio n e dg e Bo dy L e ng th (m) 1.1 F ina l Ma ss (kg ) 3.2 Pa ylo a d Ba y 49x8.9x10 Dime nsio ns (c m) Ma ximum F lig ht 67 T ime (min) Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults 14 E ng ine e ring Ma na g e me nt

SO FT WARE BASELI NE DESI G N FL I G HT MO DE SWI T C H 15

SO FT WARE BASELINE DESIG N MO DIFIED AUT O PILO T 16

BASE L I NE DE SI GN CHANGE S Design Change R eason for Change Impac t on Design Optic a l flo w c a me ra a nd L iDAR no t No t c o nfide nt in la nding s. Ro ug h Othe r se nso rs use d fo r po sitio na l use d fo r te sting la nding e nviro nme nt. e stima tio ns we re suffic ie nt to minimize e rro r the re fo re the re wa s no major effec t fro m this de sig n c ha ng e So lid no se c o ne wa s use d fo r fina l Orig ina l no se c o ne (c le a r pla stic a nd Sinc e the so lid no se c o ne is o pa que , te sting fo a m) wa s de stro ye d o n a fa ile d ta ke the HD c amer a c ould no longer be o ff a tte mpt a nd 3-D printing a used , but tha t does not effec t mission re pla c e me nt wa s fa ste r tha n o rde ring suc c ess a ne w c o ne Ma in wing spa r wa s re pla c e d with Orig ina l spa r wa s da ma g e d o n ro ug h 20g inc re a se in fina l ma ss a nd better bra ss ro d la nding a nd a re pla c e me nt c o uld str uc tur al stability of the wing. no t be o rde re d in time Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults 17 E ng ine e ring Ma na g e me nt

T E ST OVE RVI E W Syste ms Pro je c t Ove rvie w De sig n T e st Ove rvie w T e st Re sults E ng ine e ring Ma na g e me nt 18